GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 50,000 Max Cl/Cd: 32.21 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiif-il-50000-n5.txt Download as CSV file: xf-giiif-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4537 0.08986 0.08341 -0.0183 1.0000 0.0550
-8.750 -0.4572 0.08519 0.07879 -0.0199 1.0000 0.0529
-8.500 -0.5621 0.09209 0.08541 -0.0155 1.0000 0.0554
-8.250 -0.5639 0.08740 0.08077 -0.0182 1.0000 0.0528
-7.750 -0.5719 0.07668 0.06983 -0.0261 1.0000 0.0456
-7.500 -0.5671 0.07243 0.06554 -0.0264 1.0000 0.0448
-7.250 -0.5624 0.06818 0.06120 -0.0269 1.0000 0.0441
-7.000 -0.5566 0.06393 0.05681 -0.0273 1.0000 0.0434
-6.750 -0.5493 0.05973 0.05241 -0.0273 1.0000 0.0429
-6.500 -0.5404 0.05562 0.04805 -0.0270 1.0000 0.0425
-6.250 -0.5300 0.05163 0.04375 -0.0264 1.0000 0.0423
-6.000 -0.5180 0.04780 0.03957 -0.0255 1.0000 0.0424
-5.750 -0.5044 0.04424 0.03552 -0.0242 1.0000 0.0441
-5.250 -0.4737 0.03822 0.02867 -0.0214 1.0000 0.0488
-5.000 -0.4557 0.03549 0.02556 -0.0199 1.0000 0.0501
-4.750 -0.4360 0.03293 0.02259 -0.0185 1.0000 0.0518
-4.500 -0.4143 0.03054 0.01977 -0.0171 1.0000 0.0543
-4.250 -0.3917 0.02861 0.01737 -0.0158 1.0000 0.0604
-4.000 -0.3701 0.02711 0.01577 -0.0147 1.0000 0.0677
-3.750 -0.3439 0.02534 0.01367 -0.0136 1.0000 0.0738
-3.500 -0.3205 0.02421 0.01241 -0.0125 1.0000 0.0869
-3.250 -0.2973 0.02303 0.01111 -0.0115 1.0000 0.1019
-3.000 -0.2765 0.02198 0.01006 -0.0103 1.0000 0.1205
-2.750 -0.2584 0.02109 0.00918 -0.0089 1.0000 0.1463
-2.500 -0.2408 0.02015 0.00836 -0.0075 1.0000 0.1821
-2.250 -0.2242 0.01864 0.00751 -0.0064 1.0000 0.2851
-2.000 -0.0569 0.01731 0.00750 -0.0254 1.0000 1.0000
-1.750 -0.0517 0.01724 0.00732 -0.0223 1.0000 1.0000
-1.500 -0.0495 0.01722 0.00719 -0.0186 1.0000 1.0000
-1.250 -0.0488 0.01723 0.00706 -0.0147 1.0000 1.0000
-1.000 -0.0473 0.01727 0.00698 -0.0110 1.0000 1.0000
-0.750 -0.0434 0.01734 0.00692 -0.0077 1.0000 1.0000
-0.500 -0.0289 0.01747 0.00689 -0.0064 0.9976 1.0000
-0.250 0.0070 0.01767 0.00692 -0.0090 0.9885 1.0000
0.000 0.0425 0.01789 0.00698 -0.0115 0.9793 1.0000
0.250 0.0773 0.01812 0.00711 -0.0138 0.9703 1.0000
0.500 0.1125 0.01836 0.00728 -0.0161 0.9614 1.0000
0.750 0.1490 0.01862 0.00750 -0.0186 0.9531 1.0000
1.000 0.1816 0.01887 0.00774 -0.0204 0.9432 1.0000
1.250 0.2168 0.01914 0.00802 -0.0225 0.9342 1.0000
1.500 0.2582 0.01937 0.00831 -0.0257 0.9252 1.0000
1.750 0.2961 0.01954 0.00858 -0.0279 0.9124 1.0000
2.000 0.3332 0.01967 0.00882 -0.0298 0.8986 1.0000
2.250 0.3675 0.01981 0.00909 -0.0311 0.8848 1.0000
2.500 0.3993 0.01997 0.00943 -0.0318 0.8711 1.0000
2.750 0.4299 0.02011 0.00974 -0.0321 0.8570 1.0000
3.000 0.4595 0.02025 0.01006 -0.0322 0.8425 1.0000
3.250 0.4858 0.02041 0.01042 -0.0316 0.8262 1.0000
3.500 0.5119 0.02056 0.01085 -0.0309 0.8089 1.0000
3.750 0.5388 0.02064 0.01118 -0.0300 0.7907 1.0000
4.000 0.5657 0.02065 0.01146 -0.0289 0.7710 1.0000
4.250 0.5883 0.02045 0.01150 -0.0263 0.7391 1.0000
4.500 0.6066 0.01970 0.01081 -0.0215 0.6762 1.0000
4.750 0.6223 0.01932 0.01027 -0.0168 0.5784 1.0000
5.000 0.6353 0.01983 0.01006 -0.0123 0.4088 1.0000
5.250 0.6421 0.02193 0.01098 -0.0093 0.2160 1.0000
5.500 0.6523 0.02434 0.01247 -0.0074 0.1197 1.0000
5.750 0.6686 0.02610 0.01413 -0.0058 0.0963 1.0000
6.000 0.6865 0.02772 0.01573 -0.0044 0.0802 1.0000
6.250 0.7065 0.02927 0.01737 -0.0032 0.0687 1.0000
6.500 0.7313 0.03105 0.01940 -0.0020 0.0628 1.0000
6.750 0.7562 0.03302 0.02158 -0.0011 0.0569 1.0000
7.000 0.7803 0.03518 0.02403 -0.0003 0.0503 1.0000
7.250 0.8044 0.03775 0.02694 0.0005 0.0470 1.0000
7.500 0.8258 0.04063 0.03017 0.0015 0.0448 1.0000
7.750 0.8437 0.04399 0.03378 0.0024 0.0429 1.0000
8.000 0.8565 0.04738 0.03775 0.0040 0.0408 1.0000
8.250 0.8657 0.05082 0.04181 0.0057 0.0385 1.0000
8.500 0.8714 0.05462 0.04611 0.0072 0.0373 1.0000
8.750 0.8731 0.05873 0.05065 0.0087 0.0370 1.0000
9.000 0.8704 0.06295 0.05524 0.0099 0.0369 1.0000
9.250 0.8634 0.06723 0.05983 0.0109 0.0369 1.0000
9.500 0.8521 0.07152 0.06435 0.0115 0.0371 1.0000
9.750 0.8364 0.07576 0.06875 0.0117 0.0373 1.0000
10.000 0.8192 0.08063 0.07373 0.0102 0.0377 1.0000
10.250 0.8022 0.08631 0.07949 0.0071 0.0381 1.0000
10.500 0.7871 0.09284 0.08606 0.0027 0.0386 1.0000
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Polar data table (+)
Polar graphs
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